EP1843030A2 - Durchflusssteuervorrichtung - Google Patents

Durchflusssteuervorrichtung Download PDF

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Publication number
EP1843030A2
EP1843030A2 EP20070250953 EP07250953A EP1843030A2 EP 1843030 A2 EP1843030 A2 EP 1843030A2 EP 20070250953 EP20070250953 EP 20070250953 EP 07250953 A EP07250953 A EP 07250953A EP 1843030 A2 EP1843030 A2 EP 1843030A2
Authority
EP
European Patent Office
Prior art keywords
fluid flow
control device
flow control
nozzle
arrangement
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP20070250953
Other languages
English (en)
French (fr)
Other versions
EP1843030B1 (de
EP1843030A3 (de
Inventor
Barry Norman Hocking
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Rolls Royce PLC filed Critical Rolls Royce PLC
Publication of EP1843030A2 publication Critical patent/EP1843030A2/de
Publication of EP1843030A3 publication Critical patent/EP1843030A3/de
Application granted granted Critical
Publication of EP1843030B1 publication Critical patent/EP1843030B1/de
Ceased legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/105—Final actuators by passing part of the fluid
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/06—Varying effective area of jet pipe or nozzle
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/40—Nozzles having means for dividing the jet into a plurality of partial jets or having an elongated cross-section outlet
    • F02K1/42—Nozzles having means for dividing the jet into a plurality of partial jets or having an elongated cross-section outlet the means being movable into an inoperative position
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/46—Nozzles having means for adding air to the jet or for augmenting the mixing region between the jet and the ambient air, e.g. for silencing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/08—Plants including a gas turbine driving a compressor or a ducted fan with supplementary heating of the working fluid; Control thereof
    • F02K3/105—Heating the by-pass flow
    • F02K3/115—Heating the by-pass flow by means of indirect heat exchange
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/06—Varying effective area of jet pipe or nozzle
    • F02K1/12—Varying effective area of jet pipe or nozzle by means of pivoted flaps
    • F02K1/1207—Varying effective area of jet pipe or nozzle by means of pivoted flaps of one series of flaps hinged at their upstream ends on a fixed structure
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/06—Varying effective area of jet pipe or nozzle
    • F02K1/12—Varying effective area of jet pipe or nozzle by means of pivoted flaps
    • F02K1/123—Varying effective area of jet pipe or nozzle by means of pivoted flaps of two series of flaps, both having their flaps hinged at their upstream ends on a fixed structure
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/327—Application in turbines in gas turbines to drive shrouded, high solidity propeller
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/29—Three-dimensional machined; miscellaneous
    • F05D2250/292—Three-dimensional machined; miscellaneous tapered
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T137/00—Fluid handling
    • Y10T137/2278—Pressure modulating relays or followers
    • Y10T137/2409—With counter-balancing pressure feedback to the modulating device

Definitions

  • This invention relates to fluid flow control devices for use in gas turbine engines.
  • Embodiments of the invention relate to control devices for adjusting the cross-sectional area of exhaust nozzles of gas turbine engines. Further embodiments relate to controlling the flow through a heat exchanger of a gas turbine engine.
  • a fluid flow control device comprising a guide member to guide a fluid passing through a duct, the guide member being movable between first and second positions; and an urging arrangement capable of providing an urging force to urge the guide member towards the first position, characterised in that the urging arrangement is a resilient torsion bar that is formed so as to allow the guide member to be moved towards the second position by a pressure force exceeding and opposite to the urging force, the pressure force being provided by a pressure difference across the guide member.
  • the urging arrangement may be generally circular in configuration to extend around the fluid flow path.
  • a plurality of guide members may be arranged adjacent one another around the urging arrangement.
  • the urging arrangement comprises a plurality of resilient members arranged one after the other in an annular arrangement.
  • Each resilient member may have a discrete guide member mounted thereon.
  • the first position of the guide member may provide a minimum area condition for the fluid path.
  • the second position may provide a maximum area of condition for the fluid path.
  • the guide member may comprise a tapering member tapering from a wide region adjacent the urging arrangement, to a narrow region spaced from the urging arrangement.
  • the guide member tapers inwardly in a downstream direction of the flow of fluid.
  • a securing arrangement may be provided to secure the guide member to the urging arrangement.
  • the securing arrangement may comprise a clamp.
  • the securing arrangement may comprise first and second clamps.
  • a conduit defines the fluid flow path, and a fixing element may be provided to fix the fluid flow control device to the conduit.
  • the fixing element may extend in an upstream direction from the urging arrangement fixing to the conduit.
  • the fixing element may comprise an elongate member.
  • a stop may be provided to restrict the extent of movement of the guide member when urged towards the first position to provide, in one embodiment, a minimum exit area of a nozzle.
  • a second stop member may be provided to restrict the extent of travel of the guide member when being urged towards the second position, to provide, in one embodiment, a maximum nozzle exit area.
  • a damper may be provided to inhibit the speed at which the guide member moves between the first and second positions.
  • the resilient torsion bar may comprise a Shape Memory Material.
  • the assembly comprises fixed and moveable guide members alternately spaced to one another.
  • the guide members have lateral edges that are angled to abut one another to provide positive location in the first or second position.
  • a nozzle arrangement comprising a nozzle though which a fluid can flow, the nozzle having an outlet, and the arrangement further comprising an fluid flow control device as described above arranged on the nozzle at the outlet.
  • the adjustment arrangement can adjust the outlet area of the nozzle between the first and second positions.
  • the nozzle arrangement may comprise a plurality of guide members arranged circumferentially around the outlet of the nozzle.
  • Each guide member may be mounted on a common urging arrangement, which may extend around the nozzle.
  • the nozzle arrangement comprises a plurality of guide members arranged adjacent one another around the urging arrangement.
  • the fluid flow control device comprises a discrete guide member arranged on a discrete urging arrangement.
  • a plurality of the aforesaid discrete guide members and respective discrete urging arrangements may be circumferentially arranged adjacent one another.
  • a heat exchanger comprising a first inlet, a first outlet, a second inlet and a second outlet wherein at least one of the inlets and outlets comprises an fluid flow control device as described above.
  • a gas turbine engine comprising a fan for directing a first flow of air through a first nozzle, and a turbine arrangement for directing a second flow of air through a second nozzle, a first fluid flow control device as described above provided on the first nozzle, and a second fluid flow control device as described above provided on the second nozzle.
  • the temperatures and pressures of the flows of gas through the first and second nozzle may be different, and the urging arrangement of the first fluid flow control device may be selected to be appropriate for the conditions of a gas flowing through the first nozzle.
  • the second urging arrangement may be selected to be appropriate for the conditions at the second nozzle.
  • a gas turbine engine is generally indicated at 10 and comprises, in axial flow series, an air intake 11, a propulsive fan 12, an intermediate pressure compressor 13, a high pressure compressor 14, combustion equipment 15, a high pressure turbine 16, an intermediate pressure turbine 17, a low pressure turbine 18 and a variable area core exhaust hot nozzle 19 and a variable area cold bypass nozzle 21.
  • the engine 10 is surrounded by a nacelle 9 which defines a bypass duct 8 and the bypass nozzle 21.
  • the gas turbine engine 10 works in a conventional manner so that air entering the intake 11 is accelerated by the fan 12 which produce two air flows: a first air flow into the intermediate pressure compressor 13 and a second air flow which provides propulsive thrust through the cold nozzle 21.
  • the intermediate pressure compressor compresses the air flow directed into it before delivering that air to the high pressure compressor 14 where further compression takes place.
  • the compressed air exhausted from the high pressure compressor 14 is directed into the combustion equipment 15 where it is mixed with fuel and the mixture combusted.
  • the resultant hot combustion products then expand through, and thereby drive, the high, intermediate and low pressure turbines 16, 17 and 18 before being exhausted through the hot nozzle 19 to provide additional propulsive thrust.
  • the high, intermediate and low pressure turbine 16, 17 and 18 respectively drive the high and intermediate pressure compressors 14 and 13, and the fan 12 by suitable interconnecting shafts 20.
  • Fig 2 shows a close up of the rear region of the engine 10 shown in Fig 1.
  • Fig 2 shows an outer cold nozzle 22 and an inner hot nozzle 24.
  • Gas from the fan 12 is exhausted from the engine 10 via the outer nozzle 22.
  • Gas passing through the core of the engine, namely the compressors 13, 14, the combustor 15 and the turbines 16, 17, 18, is exhausted of the inner nozzle 24.
  • the gas leaving via the inner nozzle 24 is hotter than the gas leaving the outer nozzle 22.
  • the outer nozzle 22 is provided with an outer fluid flow control device 26, and the inner nozzle 24 is provided with an inner fluid flow control device 28.
  • Each of the fluid flow control devices 26, 28 comprises a plurality of guide members 30.
  • Figs 3, 4, 5, 8 and 9 show five embodiments of the outer fluid flow control device 26, but it will be appreciated that a similar construction is provided for the inner adjustment arrangement 28.
  • a guide member 30 is mounted on an urging arrangement in the form of a torsion bar 32.
  • the torsion bar 32 extends circumferentially around the outer nozzle 22, and a plurality of the guide members 30 are mounted thereon adjacent to one another in a circumferential sequence around the torsion bar 32.
  • the torsion bar 32 exerts an urging force F1 on the guide members 30 to urge them to a minimum area, or closed, position, as shown in Fig 2.
  • Each of the guide members 30 of a trapezoidal configuration and tapers in the downstream direction, having a thicker edge 34 adjacent the torsion bar 32 and a thinner edge 36 spaced from the torsion bar 32.
  • Each of the guide members 30 is fixedly mounted to the torsion bar 32 by clamping arrangements 38.
  • An elongate fixing member 40 secures the torsion bar 32 in the region of each guide member 30 to the main body of the nozzle.
  • the inner and outer nozzle adjustment arrangements 26, 28 can be seen viewed on the line IV-IV of Fig 2.
  • the guide members 30 are arranged around the core (inner) and bypass (outer) nozzle torsion bars 32 and are shown projecting into the exhaust gas streams to give a minimum nozzle area configuration particularly suitable for aircraft cruise.
  • the pressure difference is such that the guide members 30 are forced radially outwardly to increase the nozzle area.
  • the mean velocity of the working fluid decreases, relative to a fixed geometry nozzle, thereby reducing jet noise generated in a turbulent shear layer between adjacent jets and ambient.
  • a decrease in relative jet velocities has a corresponding decrease in jet noise. Jet noise is further reduced as vortices are generated from the guide members 30, which enhances mixing of the shear layers.
  • a minimum area stop member 42 is provided on the radially inner side of each guide member 30 and prevents movement of the respective guide member 30 beyond a first position, as shown in broken lines in Fig 5, to limit the minimum nozzle exit area.
  • a respective damping arrangement 44 is provided on the torsion bar in the region of at least some of the guide members 30 to ensure that movement of the guide member 30 occurs at the desired rate.
  • a maximum area stop member 45 is provided on the radially outer side of each guide member 30 and prevents movement of the respective guide member 30 beyond a second position, as shown in solid lines in Fig 5, to limit the maximum nozzle exit area.
  • the urging force F1 on the guide members 30 of the outer fluid flow control device 26 are different to the urging force F1 on the guide members 30 of the inner fluid flow control device 28.
  • the torsion bars 32 have the property that the urging forces exerted thereby increase as the torsion bars are twisted away from their relaxed condition.
  • the urging forces F1 increase until the forces F1 equal the forces F2.
  • the guide members 30 can be held in any position between the maximum area positions shown in Fig 9A and the minimum area positions shown in Fig 9B.
  • torsion bars 32 used for the inner and outer adjustment arrangements 26, 28 respectively will need to be different from each other and for different engines. It will be a simple matter for those skilled in the art to calculate the exact nature of the respective torsion bars 32 to be used.
  • the torsion bar is pre-stressed to bias it to one of the first or second positions. It is desirable to pre-stress the torsion bar to the maximum nozzle area position so that in the event of mechanical failure the maximum nozzle area, required at least for take-off, is available. Alternatively, it is preferable to pre-stress the torsion bar to the minimum nozzle area position to ensure efficiency during cruise.
  • the torsion bar comprises a Shape Memory Material (SMM) such that its Young's modulus change, at its temperature transition point, assists the pressure differential change to move the guide members 30 between their first and second positions.
  • SMM Shape Memory Material
  • the torsion bar will still be pre-stressed to the first position.
  • the SMM properties can be manipulated such that the transition point coincides with a desired altitude, for example, so that the torsion bar deforms to the second position at and above that altitude, for example where jet noise is no longer problematic.
  • the SMM torsion bar deforms back to its original configuration in the first position.
  • the torsion bar may be pre-stressed to the second position and transition to the first position at the desired altitude. Another parameter may be used instead of altitude.
  • the SMM may comprise a Shape Memory Alloy as known in the art.
  • the SMM may be temperature controlled by supplying heat from a source such as electrical heating wires or from a dedicated hot air ducting, e.g. from the IP or HP compressors.
  • the SMM torsion bar may comprise a solid bar or a hollow tube. The latter is particularly advantageous when controlled using hot air ducting since it becomes its own duct.
  • Selective temperature changes to the SMM provides assistance to gas loading to move the guide members 30.
  • the stiffness of the torsion bar 32 changes above and below the temperature transition point of the SMM, therefore enabling the gas loads to move the members 30 more easily at certain conditions.
  • FIG 6 A further embodiment of the torsion bar is shown in Fig 6 wherein the torsion bar 32 comprises a first material core 46 surrounded by an SMM 48 such that the first material 46 and the SMM 48 are coaxially arranged.
  • the two materials 46, 48 are pre-stressed in opposition to each other so that when the transition point is crossed, the SMM 48 rotates the attached guide members 30 (not shown for clarity) to their deployed positions.
  • the first material 46 acts to assist the return of the arrangement to the non-deployed position when the transition point is crossed in the opposite direction thereby negating any hysteresis effects.
  • This arrangement is advantageous because the first material 46 experiences lower stresses than the SMM 48, in accordance with their capacity to be stressed. It may also be possible to remove at least one of the stop members 42, 45 due to the first material 46 and the SMM 48 acting in opposition to each other.
  • the torsion bar 32 comprises a first material core 46 with a strip or wire 50 of SMM wound around the core 46 to form a helix or coil.
  • This arrangement provides for less stress in the torsion bar 32.
  • a further advantage can be realised by designing the coils of SMM 50 to be coil bound when the guide members 30 are in the deployed position so that the SMM 50 coil itself performs the function of an end stop.
  • the SMM coils 50 may be designed to be coil bound when the guide members 30 are in the non-deployed position.
  • Figs 8A and 8B are schematic perspective diagrams of some of the plurality of guide members 30 in an alternative arrangement to Fig 5.
  • This alternative arrangement comprised fixed and moveable guide members 30a, 30 alternately spaced to one another.
  • Adjacent guide members 30, 30a are shaped to abut at their lateral edges 131, 132 to provide a stop function without requiring the separate stop members 42, 45 of Fig 5.
  • Alternate guide members 30a are fixed in their alignment whilst the other guide members 30 are free to move between the first and second positions as previously described.
  • the guide members 30 move from the second, open position (Fig 8B) to the first, closed position (Fig 8A) the angled abutting edges 131, 132 of the guide members 30, 30a act as the stop member.
  • a stop member may be added to provide a positive and known rotation into the deployed / second position.
  • Fig 10 shows a further application of the fluid flow control device to control flow through a heat exchanger 52 within a gas turbine engine 10.
  • the heat exchanger 52 comprises a first inlet 54 in fluid communication with a first outlet 56 through which flows a first fluid as indicated by arrows 58.
  • the heat exchanger 52 also comprises a second inlet 60 in fluid communication with a second outlet 62 through which flows a second fluid as indicated by arrows 64.
  • heat exchange occurs between the first and second fluid flows 58, 64 within the heat exchanger 52.
  • the first flow 58 may be extracted from a compressor stage 13, 14 and the second flow 64 be extracted from the bypass duct 21 so that the first flow 58 is cooled by its proximity with the second, cooler flow 64.
  • the second inlet 60 and second outlet 62 are shown in Fig 10 in fluid communication with a duct 66, for example the bypass duct 8.
  • a first fluid flow control device 68 according to the present invention is provided at the junction of the second outlet 62 and the duct 66.
  • This comprises a door 70 attached to a torsion bar 72 and is operable in the same manner as previously described with reference to other embodiments of the present invention.
  • the torsion bar 72 is pre-stressed to provide an urging force F1 which opposes the pressure force F2.
  • a second fluid flow control device 74 may be provided at the junction of the second inlet 60 and the duct 66. This would act in the same manner as the first fluid flow control device 68; hence the two fluid flow control devices 68, 74 would move in approximate synchronicity.
  • the second flow 64 has been described in fluid communication with the duct 66 and controlled by fluid flow control devices 68, 74 according to the present invention
  • the first flow 58 could be in fluid communication with the duct 66 instead.
  • the fluid flow control device may be provided on any one or combination of the inlets and outlets of the heat exchanger 52. Other modifications will be obvious to the skilled reader.
  • GB/2,374,121/B of the present Applicant provides guide members or tabs that are deployable for noise reduction purposes.
  • the teachings of GB 2,374,121 B are hereby incorporated by reference.
  • the present invention provides a novel actuation method which has particular advantages in reducing the complexity and weight of the noise reduction fluid flow control device over prior assemblies.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Control Of Turbines (AREA)
  • Safety Valves (AREA)
EP07250953.2A 2006-04-05 2007-03-07 Durchflusssteuervorrichtung Ceased EP1843030B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB0606823A GB0606823D0 (en) 2006-04-05 2006-04-05 Adjustment assembly

Publications (3)

Publication Number Publication Date
EP1843030A2 true EP1843030A2 (de) 2007-10-10
EP1843030A3 EP1843030A3 (de) 2011-02-23
EP1843030B1 EP1843030B1 (de) 2015-09-16

Family

ID=36539349

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07250953.2A Ceased EP1843030B1 (de) 2006-04-05 2007-03-07 Durchflusssteuervorrichtung

Country Status (3)

Country Link
US (1) US8122723B2 (de)
EP (1) EP1843030B1 (de)
GB (1) GB0606823D0 (de)

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WO2008045064A1 (en) * 2006-10-12 2008-04-17 United Technologies Corporation Turbofan engine sound control system and method
EP2455584A1 (de) * 2010-11-19 2012-05-23 Alstom Technology Ltd Gasturbine mit Steuerungsmittel zur Kühlung, welche teilweise aus einer Gedächtnislegierung bestehen
EP2074310B1 (de) * 2006-10-12 2015-06-17 United Technologies Corporation Steuerung des aerodynamischen widerstands eines turbinentriebwerks während eines abschaltzustands

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US7963099B2 (en) * 2007-05-21 2011-06-21 General Electric Company Fluted chevron exhaust nozzle
FR2928183A1 (fr) * 2008-02-29 2009-09-04 Aircelle Sa Dispositif de reduction de bruit pour moteur d'aeronef, du type a chevrons mobiles
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US8910465B2 (en) 2009-12-31 2014-12-16 Rolls-Royce North American Technologies, Inc. Gas turbine engine and heat exchange system
US10329945B2 (en) * 2015-04-21 2019-06-25 Siemens Energy, Inc. High performance robust gas turbine exhaust with variable (adaptive) exhaust diffuser geometry
GB201718796D0 (en) 2017-11-14 2017-12-27 Rolls Royce Plc Gas turbine engine having an air-oil heat exchanger
US11286881B2 (en) * 2019-10-16 2022-03-29 Rolls-Royce North American Technologies Inc. Gas turbine engine with reversible heat exchanger
US11492998B2 (en) * 2019-12-19 2022-11-08 The Boeing Company Flexible aft cowls for aircraft
US11724815B2 (en) * 2021-01-15 2023-08-15 The Boeing Company Hybrid electric hydrogen fuel cell engine

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Also Published As

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US8122723B2 (en) 2012-02-28
GB0606823D0 (en) 2006-05-17
EP1843030B1 (de) 2015-09-16
EP1843030A3 (de) 2011-02-23
US20070235080A1 (en) 2007-10-11

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